CN104912668A - Variable camber vane type spiral flow distortion generator - Google Patents
Variable camber vane type spiral flow distortion generator Download PDFInfo
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- CN104912668A CN104912668A CN201510199348.2A CN201510199348A CN104912668A CN 104912668 A CN104912668 A CN 104912668A CN 201510199348 A CN201510199348 A CN 201510199348A CN 104912668 A CN104912668 A CN 104912668A
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Abstract
The invention discloses a variable camber vane type spiral flow distortion generator, and belongs to the aviation and aerospace fields. The variable camber vane type spiral flow distortion generator comprises a circular ring-shaped casing, two vane groups symmetrically arranged in the casing, and two vane group driving mechanism respectively driving the two vane groups to independently rotate, and each of the vane groups is formed by a plurality of variable camber vanes; each of the variable camber vanes comprises a front vane and a rear vane which are movably connected; the front vane is fixed on the casing, and the rear vane traverses through the casing and is connected with the corresponding vane group driving mechanism; and the vane group driving mechanism can drive the rear vanes to rotate. The structure of spiral flow can be changed by adjusting the installation angles of the rear vanes of the variable camber vanes to form homodromous integral vortex, reverse direction integral vortex, biased pair vortex and other different forms of vortex, and the spiral flow intensity of the spiral flow distortion can be adjusted in real time; and the vanes can be replaced in the experiment process without shut-down to complete engine test under various spiral flow distortions, so the test cost is reduced, the test time is shortened, and the test efficiency is improved.
Description
Technical field
The present invention relates to a kind of swirl flow distortion generator, be specifically a kind of variable camber blade type swirl flow distortion generator, belong to aerospace field.
Background technique
At present, advanced opportunity of combat many employings belly and both sides air inlet, motor is placed in afterbody, and for improving total pressure recovery coefficient and taking into account stealthy demand, Design of Inlet becomes S shape.During special circumstances such as carrying out maneuvering flight at fighter, meet with crosswind, launch a guided missile, except producing total pressure distortion or total temperature distortion, also swirl flow distortion can be formed.The intensity of swirl flow distortion is except outside the Pass having with the shape of intake duct, also can be subject to the impact of flying condition and attitude, binary belly S shape intake duct as aircraft is very responsive for flight angle of sideslip, can produce when angle of sideslip is greater than 6 ° and turn to identical overall whirlpool with motor, its maximum swirl strength reaches 5 °, and average swirl strength is also more than 2.5 °.For research swirl flow distortion is on the impact of engine performance and stability, researcher has developed the swirl flow distortion generator of various ways for simulating swirl flow distortion.Blade type swirl flow distortion generator is widely used because it possesses the advantages such as structure is simple, cost is low, easy to adjust.
The end of the eighties in last century, Germany Fottner etc. swirl flow distortion is studied, developed a kind of delta wing swirl flow distortion generator, manually the angle of the adjusting triangle wing and incoming flow produce varying strength to whirlpool; 2002, AEDC devised a kind of blade type swirl flow distortion generator, and utilize the wake's flow field of blade and the leakage vortex of end to produce eddy flow, experiment creates the eddy flow tangentially reaching 25 °; Peng Chengyi, Lin Feng of Nanjing Aero-Space University and a Kun unit etc.
[1-3]successively confirm that blade type swirl flow distortion generator can produce basic Swirling Flow by experiment; Jiang Jian etc.
[4]devise the blade type swirl flow distortion generator that a kind of blade deflection angle, blade height and the number of blade can manually be changed, numerical simulation and experimental study different designs parameter is on the impact of swirl flow distortion structure and intensity, prove that this swirl generator can produce overall whirlpool, the whirlpool and to whirlpool, local of varying strength, cutting angle maximumly reaches 28 °.Existing blade type swirl flow distortion generator adopts conventional integral blade, the mode that can only manually regulate is changed the established angle of whole blade or is realized the adjustment of swirl strength and structure by the blade changing different bent angle, complicated operation and a large amount of time need be spent for adjusting blade, affects test efficiency.Meanwhile, be subject to the restriction of integral blade self aeroperformance, generally established angle adjustment range exceed ± 10 ° just there will be boundary layer be separated, cannot ensure that air-flow flows along blade profile, cause swirl strength cannot continue increase.
Reference:
[1] Peng Chengyi, Lin Feng, a Kun unit. DESIGN OF SWIRL SIMULATORS [J]. aviation power journal, 1986,1 (2): 22-26;
[2] Lin Feng. eddy flow simulation technique research [D]. Nanjing: Nanjing Aero-Space University, 1992;
[3] Peng Chengyi, Ma Jiaju, Yin Junfei. new machine take a flight test in intake duct eddy flow measure [J]. Push Technology, 1994,15 (4): 8-13;
[4] Jiang Jian, Qu Jiyun, Shi Jianbang. the design of intake duct swirl generator and numerical simulation [J]. gas turbine Testing and research, 2008,21 (1): 43-46.
Summary of the invention
Technical problem to be solved by this invention is to overcome prior art defect, and eddy currents is various, strength of vortex regulates automatically to provide one to produce, and blade exchanging is variable camber blade type swirl flow distortion generator easily.
In order to solve the problems of the technologies described above, one provided by the invention variable camber blade type swirl flow distortion generator, comprises ring casing, two vane group driving mechanisms that symmetry is arranged on two groups of vane group be made up of several variable curved blades in casing and drives two groups of vane group independently to rotate respectively; Described variable camber leaf packet draws together the front vane and rear blade that are flexibly connected each other; Described front vane is fixed on casing, and described rear blade is connected with vane group driving mechanism through casing; Described vane group driving mechanism can drive rear blade to rotate.
In the present invention, described vane group driving mechanism comprises interlock semi-ring, drive motor and some rocking arms; Described interlock semi-ring is arranged on casing periphery and is connected with drive motor, and one end of described some rocking arms is connected with interlock semi-ring, and the other end is connected with rear blade respectively; Above-mentioned drive motor adopts stepper motor.
In the present invention, the quantity of described variable curved blades is 1-12.
In the present invention, the rotation angle of described rear blade is ± 30 °.
In the present invention, described front vane is the 30-40% of vane overall length, and rear blade is the 60-70% of vane overall length.
Beneficial effect of the present invention is: (1), the present invention adopt variable curved blades, by regulating the setting angle of rear blade, the structure of eddy flow can be changed, produce overall in the same way whirlpool, reverse overall whirlpool, to whirlpool, be biased multi-form eddy current such as whirlpools, and the swirl flow distortion of strength of vortex can be adjusted in real time; (2), the quantity of variable curved blades adopts 1-12, can require adjustment blade quantity, greatly improve the trial stretch of swirl flow distortion generator according to actual tests; (3), the rotation angle of stating rear blade is ± 30 °, can ensure that rear blade there will not be obvious boundary layer to be separated in adjustment, guarantee that air-flow flows along blade profile, maximumly makes overall whirlpool and equals 30 ° and 60 ° respectively to the intensity in whirlpool; (4), front vane is the 30-40% of vane overall length, rear blade is the 60-70% of vane overall length, adopt the variable camber blade aerodynamic performance of this front and back length of blade allocation proportion good, can ensure that rear blade is in the slewing area of ± 30 °, air-flow flows along blade profile, there will not be the phenomenon that boundary layer is separated; (5), in experimentation need not shut down replacing blade, complete the engine test under multiple swirl flow distortion, reduce experimentation cost and time, improve test efficiency; (6), driving mechanism structure is simple and reliable, and adopt the real-time control of stepper motor, can simulate the dynamic formation process of swirl flow distortion and the impact on motor, its control accuracy is high, greatly can improve the accuracy of test data.
Accompanying drawing explanation
Fig. 1 is the present invention's variable camber blade type swirl flow distortion generator architecture figure;
Fig. 2 is A-A sectional view in Fig. 1;
Fig. 3 is B-B sectional view in Fig. 1;
Fig. 4 is variable camber blade structure schematic diagram in the present invention, and (a) is plan view, (b) is side view;
Fig. 5 is variable camber leaf cross-section schematic diagram, and (b) is variable curved blades original state, and (a) represents that rear blade is rotated counterclockwise, and (c) represents that rear blade turns clockwise.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in Fig. 1 to 5, variable camber blade type swirl flow distortion generator of the present invention, comprises casing 1, variable curved blades 2, two interlock semi-ring 3 and two stepper motors 4 and forms.Casing 1 is cirque structure, and variable curved blades 2 is two groups, and often group is made up of 6 variable curved blades 2, and first group comprises blade A1-A6, and second group comprises blade B1-B; Two groups of variable curved blades 2 symmetries are arranged in casing 1, the installation direction of variable curved blades 2 and the axial consistent of casing 1; The variable curved blades 2 of each group is arranged along casing 1 inner circumferential uniform intervals.
Shown in Figure 4 and 5, variable curved blades 2 comprises front vane 2-1 and rear blade 2-2, and wherein front vane 2-1 accounts for the 30-40% of total length of blade, and rear blade 2-2 accounts for the 60-70% of total length of blade, and the gap between two blades accounts for 1% of total length of blade.The dead axle of front vane 2-1 is bolted on casing 1 through casing 1, unadjustable after installation; The rotatingshaft of rear blade 2-2 realizes being flexibly connected with casing 1 by pin is fixing through casing 1.Two interlock semi-rings 3 are arranged on the periphery of casing 1, respectively corresponding two groups of vane group.The rotatingshaft of the rear blade 2-2 in each variable curved blades 2 is connected with interlock semi-ring 3 respectively by rocking arm 7.
Interlock semi-ring 3 is connected with the first push rod 5 by pin, and the first push rod 5 is connected with the second push rod 8 by pin, and the second push rod 8 is connected by the output shaft of key with stepper motor 4.When stepper motor 4 rotates, drive the second push rod 8 to rotate, and then drive the first push rod 5 to move, the first push rod 5 moves and causes interlock semi-ring 3 to move along the periphery of casing 1 simultaneously, and then drives rear blade 2-2 to realize rotating by rocking arm 7.The established angle that every platform stepper motor 4 controls rear blade 2-2 in one group of variable curved blades 2 regulates, by computer or operating platform control step motor 4, the sense of rotation of given stepper motor 4 output shaft and angle, control the size of rear blade 2-2 established angle and regulate.The angle of swing of rear blade 2-2 established angle is ± 30 °, can realize the adjustment of the bent angle size and Orientation of variable curved vane 2, to produce the eddy flow of varying strength and structural type.
As shown in Figure 5, in figure, (b) is variable curved blades 2 original state, and (a) represents that rear blade 2-2 is rotated counterclockwise, and shown in (c), rear blade 2-2 turns clockwise.Under axial admission condition, keep axial flow after blade state shown in airflow passes (b), do not produce eddy flow; Suppose that hand engine rotation is clockwise direction, then the blade state Later Zhou Dynasty, one of the Five Dynasties shown in airflow passes (a) is negative value to flow angle, and air-flow is along being rotated counterclockwise, and produce eddy flow, now eddy flow direction is contrary with hand engine rotation, is called reverse whirlpool; The blade state Later Zhou Dynasty, one of the Five Dynasties shown in airflow passes (c) to flow angle be on the occasion of, air-flow rotates clockwise, and generation eddy flow, now eddy flow direction is identical with hand engine rotation, is called whirlpool in the same way.
In the present embodiment, often organizing variable curved blades 2 quantity is 6, in actual tests process, also can carry out quantity adjustment according to actual needs.The front vane 2-1 of each variable curved blades 2 of swirl flow distortion generator and rear blade 2-2 must use in pairs, variable curved blades 2 sum minimum 1, maximum 12.
In using process, when to control two groups of variable curved blades 2 rear blade 2-2 established angles be respectively zero degree to stepper motor 4, charge air flow angle is not affected, maintain axial admission.The established angle adjusting range size of two groups of blades is identical, produce vortex flow when direction is contrary, it is 30 ° that such as the first stepping motor controls second group of blade B1-B6 established angle, and the second Electric Machine Control first group blade A1-A6 established angle is-30 °, produce swirl strength be 60 ° to vortex flow.The established angle adjusting range of two groups of blades varies in size, and direction contrary time produce biased to vortex flow, such as the first step motor control second group of blade B1-B6 established angle is 20 °, second step motor control first group blade A1-A6 established angle is-30 °, and producing swirl strength is 50 ° being biased vortex flow.The established angle adjusting range size and Orientation homogeneous phase of two groups of blades produces overall whirlpool simultaneously, and two groups of blade angles are 30 °, produces the overall in the same way whirlpool that swirl strength is 30 °; Two groups of blade angles are-30 °, produce the reverse overall whirlpool that swirl strength is 30 °; Overall vortices breakdown is changed by the size adjusting established angle.
Air-flow, by the blade of swirl flow distortion generator, forms the Secondary Flow of circumference; Just formed whirlpool when applying the Secondary Flow that both direction is contrary, intensity is identical; If only apply the Secondary Flow in a direction, then form overall whirlpool.The intensity of Secondary Flow is directly proportional to tangential gas flow angle, by regulating the established angle of variable curved blades 2 rear blade 2-2, blade bent angle is increased, when geometry Inlet cone angle is constant, outlet flow angle must be caused to rise, when not having suction surface boundary layer to be separated, bent angle is larger, tangential gas flow angle is larger, and Secondary Flow is more obvious, then swirl flow distortion intensity is also larger.Therefore variable camber blade type swirl flow distortion generator proposed by the invention; the swirl flow distortion of varying strength and structural type can be simulated easily at engine intake; need not shut down and change blade and just can carry out the test of multi-form eddy flow to engine performance and stability influence; reduce experimentation cost and time; it not only can be directly used in the test of aeroengine swirl flow distortion, also can be applicable to the test of gas compressor swirl flow distortion.
The above is only the preferred embodiment of the present invention, it should be pointed out that for those skilled in the art, can also make some improvement under the premise without departing from the principles of the invention, and these improvement also should be considered as protection scope of the present invention.
Claims (5)
1. a variable camber blade type swirl flow distortion generator, is characterized in that: comprise ring casing, two vane group driving mechanisms that symmetry is arranged on two groups of vane group be made up of several variable curved blades in casing and drives two groups of vane group independently to rotate respectively; Described variable camber leaf packet draws together the front vane and rear blade that are flexibly connected each other; Described front vane is fixed on casing, and described rear blade is connected with vane group driving mechanism through casing; Described vane group driving mechanism can drive rear blade to rotate.
2. variable camber blade type swirl flow distortion generator according to claim 1, is characterized in that: described vane group driving mechanism comprises interlock semi-ring, drive motor and some rocking arms; Described interlock semi-ring is arranged on casing periphery and is connected with drive motor, and one end of described some rocking arms is connected with interlock semi-ring, and the other end is connected with rear blade respectively.
3. variable camber blade type swirl flow distortion generator according to claim 1 and 2, is characterized in that: the quantity of described blade is 1-12.
4. variable camber blade type swirl flow distortion generator according to claim 3, is characterized in that: the rotation angle of described rear blade is ± 30 °.
5. variable camber blade type swirl flow distortion generator according to claim 4, it is characterized in that: described front vane is the 30-40% of vane overall length, rear blade is the 60-70% of vane overall length.
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| CN201510199348.2A CN104912668B (en) | 2015-04-24 | 2015-04-24 | Variable camber vane type spiral flow distortion generator |
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| CN201510199348.2A CN104912668B (en) | 2015-04-24 | 2015-04-24 | Variable camber vane type spiral flow distortion generator |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106153346A (en) * | 2016-07-20 | 2016-11-23 | 南京航天航空大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107505138A (en) * | 2017-09-11 | 2017-12-22 | 南京航空航天大学 | A kind of complicated distortion generator for Compressor Stability experiment |
| CN107687948A (en) * | 2017-09-29 | 2018-02-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of inlet total pressure and distorted to vortex flow coupling generator and aberration test method |
| CN108362499A (en) * | 2017-12-26 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of detachable swirl flow distortion generator of multifunctional box |
| CN109578335A (en) * | 2018-11-27 | 2019-04-05 | 中国航发湖南动力机械研究所 | Variable camber vane type tandem stator and compressor |
| CN111175053A (en) * | 2020-01-03 | 2020-05-19 | 北京航空航天大学 | Air inlet distortion simulation device for aircraft engine |
| CN111896265A (en) * | 2020-08-06 | 2020-11-06 | 中国航空工业集团公司沈阳空气动力研究所 | Air jet type dynamic pressure distortion generator and generation method |
| CN112179659A (en) * | 2020-08-17 | 2021-01-05 | 南京航空航天大学 | Adjustable residual rotation distortion generating device based on memory alloy |
| CN112665863A (en) * | 2020-11-10 | 2021-04-16 | 西安交通大学 | Radial rotating plate type adjustable total pressure distortion generator |
| CN112729855A (en) * | 2020-12-17 | 2021-04-30 | 南京航空航天大学 | Low-unnecessary-pulsation movable plugboard type total pressure distortion generator and test method |
| CN112960139A (en) * | 2021-02-26 | 2021-06-15 | 中国人民解放军空军工程大学 | To vortex flow distortion generator |
| CN113418713A (en) * | 2021-06-21 | 2021-09-21 | 中国航发沈阳发动机研究所 | Combined distortion generator of engine |
| CN113670620A (en) * | 2021-07-26 | 2021-11-19 | 南京航空航天大学 | Novel device for generating rotational flow distortion |
| CN114013668A (en) * | 2021-11-10 | 2022-02-08 | 中国航发沈阳发动机研究所 | Aero-engine fan capable of actively adjusting electromagnetic scattering characteristics |
| CN114876637A (en) * | 2022-04-13 | 2022-08-09 | 太仓点石航空动力有限公司 | Unsteady load engine inlet total pressure distortion simulation device, method and system |
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| CN106153346B (en) * | 2016-07-20 | 2019-07-19 | 南京航空航天大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN106153346A (en) * | 2016-07-20 | 2016-11-23 | 南京航天航空大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107505138A (en) * | 2017-09-11 | 2017-12-22 | 南京航空航天大学 | A kind of complicated distortion generator for Compressor Stability experiment |
| CN107505138B (en) * | 2017-09-11 | 2019-05-14 | 南京航空航天大学 | A kind of complicated distortion generator for Compressor Stability test |
| CN107687948A (en) * | 2017-09-29 | 2018-02-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of inlet total pressure and distorted to vortex flow coupling generator and aberration test method |
| CN107687948B (en) * | 2017-09-29 | 2023-09-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet total pressure and vortex flow coupling distortion generator and distortion test method |
| CN108362499A (en) * | 2017-12-26 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of detachable swirl flow distortion generator of multifunctional box |
| CN109578335A (en) * | 2018-11-27 | 2019-04-05 | 中国航发湖南动力机械研究所 | Variable camber vane type tandem stator and compressor |
| CN111175053A (en) * | 2020-01-03 | 2020-05-19 | 北京航空航天大学 | Air inlet distortion simulation device for aircraft engine |
| CN111896265A (en) * | 2020-08-06 | 2020-11-06 | 中国航空工业集团公司沈阳空气动力研究所 | Air jet type dynamic pressure distortion generator and generation method |
| CN112179659B (en) * | 2020-08-17 | 2021-08-06 | 南京航空航天大学 | Adjustable residual rotation distortion generating device based on memory alloy |
| CN112179659A (en) * | 2020-08-17 | 2021-01-05 | 南京航空航天大学 | Adjustable residual rotation distortion generating device based on memory alloy |
| CN112665863A (en) * | 2020-11-10 | 2021-04-16 | 西安交通大学 | Radial rotating plate type adjustable total pressure distortion generator |
| CN112729855B (en) * | 2020-12-17 | 2021-10-01 | 南京航空航天大学 | Low-unnecessary-pulsation movable plugboard type total pressure distortion generator and test method |
| CN112729855A (en) * | 2020-12-17 | 2021-04-30 | 南京航空航天大学 | Low-unnecessary-pulsation movable plugboard type total pressure distortion generator and test method |
| CN112960139A (en) * | 2021-02-26 | 2021-06-15 | 中国人民解放军空军工程大学 | To vortex flow distortion generator |
| CN112960139B (en) * | 2021-02-26 | 2022-09-20 | 中国人民解放军空军工程大学 | To vortex flow distortion generator |
| CN113418713A (en) * | 2021-06-21 | 2021-09-21 | 中国航发沈阳发动机研究所 | Combined distortion generator of engine |
| CN113670620A (en) * | 2021-07-26 | 2021-11-19 | 南京航空航天大学 | Novel device for generating rotational flow distortion |
| CN113670620B (en) * | 2021-07-26 | 2022-06-17 | 南京航空航天大学 | Novel device for generating rotational flow distortion |
| CN114013668A (en) * | 2021-11-10 | 2022-02-08 | 中国航发沈阳发动机研究所 | Aero-engine fan capable of actively adjusting electromagnetic scattering characteristics |
| CN114013668B (en) * | 2021-11-10 | 2024-04-09 | 中国航发沈阳发动机研究所 | Aeroengine fan capable of actively adjusting electromagnetic scattering characteristics |
| CN114876637A (en) * | 2022-04-13 | 2022-08-09 | 太仓点石航空动力有限公司 | Unsteady load engine inlet total pressure distortion simulation device, method and system |
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